NACA 2408 (naca2408-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 200,000 Max Cl/Cd: 66.56 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2408-il-200000.txt Download as CSV file: xf-naca2408-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2408
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5291 0.10873 0.10513 -0.0095 1.0000 0.0456
-9.500 -0.5315 0.10450 0.10095 -0.0147 1.0000 0.0462
-9.250 -0.5311 0.10015 0.09664 -0.0185 1.0000 0.0464
-9.000 -0.5313 0.09548 0.09201 -0.0224 1.0000 0.0465
-8.750 -0.5356 0.08915 0.08572 -0.0219 1.0000 0.0476
-8.500 -0.5264 0.08667 0.08325 -0.0197 1.0000 0.0489
-8.250 -0.5215 0.08365 0.08025 -0.0201 1.0000 0.0503
-8.000 -0.5206 0.07999 0.07662 -0.0222 1.0000 0.0516
-7.750 -0.5179 0.07533 0.07198 -0.0269 1.0000 0.0533
-7.500 -0.5145 0.06959 0.06622 -0.0332 1.0000 0.0557
-7.250 -0.5147 0.06179 0.05796 -0.0441 1.0000 0.0592
-7.000 -0.5168 0.05445 0.05059 -0.0450 1.0000 0.0605
-6.750 -0.5019 0.05384 0.05020 -0.0421 1.0000 0.0633
-6.500 -0.4914 0.05089 0.04716 -0.0420 1.0000 0.0671
-6.250 -0.4916 0.03815 0.03357 -0.0440 1.0000 0.0500
-6.000 -0.4840 0.02727 0.02132 -0.0423 1.0000 0.0380
-5.750 -0.4648 0.02541 0.01928 -0.0413 1.0000 0.0399
-5.500 -0.4444 0.02373 0.01727 -0.0401 1.0000 0.0433
-5.250 -0.4225 0.02174 0.01479 -0.0389 1.0000 0.0455
-5.000 -0.4003 0.01933 0.01204 -0.0381 1.0000 0.0492
-4.750 -0.3776 0.01848 0.01112 -0.0373 1.0000 0.0541
-4.500 -0.3537 0.01764 0.01003 -0.0364 1.0000 0.0585
-4.250 -0.3296 0.01628 0.00861 -0.0359 1.0000 0.0641
-4.000 -0.3054 0.01565 0.00787 -0.0353 1.0000 0.0690
-3.750 -0.2809 0.01509 0.00720 -0.0347 1.0000 0.0737
-3.500 -0.2558 0.01423 0.00638 -0.0344 1.0000 0.0783
-3.250 -0.2307 0.01383 0.00595 -0.0340 1.0000 0.0848
-3.000 -0.2047 0.01321 0.00536 -0.0339 1.0000 0.0930
-2.750 -0.1785 0.01270 0.00492 -0.0338 1.0000 0.1083
-2.500 -0.1512 0.01199 0.00454 -0.0342 1.0000 0.1681
-2.250 -0.1245 0.01146 0.00443 -0.0347 1.0000 0.2675
-2.000 -0.0870 0.01090 0.00437 -0.0373 0.9967 0.3951
-1.750 -0.0495 0.00996 0.00443 -0.0396 0.9929 0.6396
-1.500 -0.0179 0.00929 0.00459 -0.0387 0.9883 0.9370
-1.250 0.0318 0.00928 0.00444 -0.0435 0.9816 1.0000
-1.000 0.0775 0.00932 0.00434 -0.0474 0.9759 1.0000
-0.750 0.1190 0.00931 0.00423 -0.0503 0.9674 1.0000
-0.500 0.1625 0.00927 0.00411 -0.0536 0.9602 1.0000
-0.250 0.2067 0.00920 0.00397 -0.0569 0.9530 1.0000
0.000 0.2450 0.00911 0.00385 -0.0590 0.9430 1.0000
0.250 0.2838 0.00900 0.00370 -0.0610 0.9336 1.0000
0.500 0.3191 0.00887 0.00355 -0.0621 0.9224 1.0000
0.750 0.3495 0.00877 0.00343 -0.0622 0.9082 1.0000
1.000 0.3776 0.00869 0.00333 -0.0617 0.8923 1.0000
1.250 0.4037 0.00864 0.00326 -0.0609 0.8739 1.0000
1.500 0.4299 0.00861 0.00319 -0.0600 0.8549 1.0000
1.750 0.4554 0.00860 0.00313 -0.0589 0.8327 1.0000
2.000 0.4799 0.00860 0.00305 -0.0576 0.8048 1.0000
2.250 0.5042 0.00866 0.00300 -0.0562 0.7728 1.0000
2.500 0.5289 0.00877 0.00302 -0.0551 0.7419 1.0000
2.750 0.5536 0.00893 0.00306 -0.0541 0.7101 1.0000
3.000 0.5779 0.00913 0.00312 -0.0530 0.6745 1.0000
3.250 0.6024 0.00935 0.00324 -0.0520 0.6390 1.0000
3.500 0.6270 0.00960 0.00338 -0.0511 0.6055 1.0000
3.750 0.6517 0.00987 0.00356 -0.0503 0.5716 1.0000
4.000 0.6762 0.01016 0.00378 -0.0496 0.5370 1.0000
4.250 0.6998 0.01052 0.00399 -0.0486 0.4909 1.0000
4.500 0.7225 0.01098 0.00423 -0.0476 0.4312 1.0000
4.750 0.7441 0.01159 0.00455 -0.0465 0.3530 1.0000
5.000 0.7603 0.01302 0.00518 -0.0449 0.1950 1.0000
5.250 0.7766 0.01479 0.00623 -0.0434 0.0894 1.0000
5.500 0.7989 0.01566 0.00708 -0.0425 0.0764 1.0000
5.750 0.8212 0.01649 0.00796 -0.0415 0.0696 1.0000
6.000 0.8438 0.01727 0.00876 -0.0406 0.0639 1.0000
6.250 0.8639 0.01851 0.01002 -0.0393 0.0600 1.0000
6.500 0.8873 0.01924 0.01086 -0.0385 0.0559 1.0000
6.750 0.9095 0.02024 0.01188 -0.0376 0.0520 1.0000
7.000 0.9302 0.02200 0.01365 -0.0365 0.0479 1.0000
7.250 0.9537 0.02321 0.01502 -0.0356 0.0446 1.0000
7.500 0.9761 0.02456 0.01647 -0.0348 0.0407 1.0000
7.750 0.9971 0.02791 0.01997 -0.0339 0.0372 1.0000
8.000 1.0191 0.02969 0.02209 -0.0326 0.0356 1.0000
8.250 1.0391 0.03179 0.02454 -0.0313 0.0334 1.0000
8.500 1.0575 0.03378 0.02678 -0.0300 0.0310 1.0000
8.750 1.0737 0.03661 0.02990 -0.0285 0.0300 1.0000
9.000 1.0857 0.04016 0.03387 -0.0266 0.0297 1.0000
9.250 1.0832 0.04638 0.04093 -0.0229 0.0316 1.0000
9.500 1.0778 0.05213 0.04720 -0.0199 0.0333 1.0000
9.750 1.0700 0.05717 0.05260 -0.0175 0.0344 1.0000
10.000 1.0588 0.06200 0.05770 -0.0153 0.0353 1.0000
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Polar data table (+)
Polar graphs
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